Aeroplane



J. G. CONNOR Nov. 5, 1929.

AEROPLANE Filed Nov. 26, 1928 3 Sheets-Sheet 1 J. G. CQNNOR Nov, 5, 1929.

AEROPLANE Filgd. Nov. 26, 1.928

3 Sheets-Sheet 2 Inventor g? faiaiwi" J. G. CONNOR Nov. 5, 1929.

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maul @FFEQE JAMES G. coNNoR, or HAItRIsBURG, PENNSYLVANIA, ASSIGNOR or ONE-tram 'ro HARRY L. REYNOLDS AND ONE-SIXTH 'ro s. 'r. nunnoox, JR, BOTH or HARRIS= BURG, PENNSYLVANIA AEROPLANE Application filed November 26, 1928. Serial No. 322,076.

The present invention relates to aeroplanes and more particularly to improvements in the controls thereof.

The prime object of the invention resides in the provision of a pair of auxiliary wings one to each side of the fuselage between the main wings and the tail structure for assisting in the control ofthe aeroplane, said auxiliary wings being controllable from the in- A still further very important object of the invention resides in the provision of auxiliary wings in an aeroplane for the purpose of permitting landing in a shorter space than is possible with the ordinary construction and to provide means for preventing the aeroplane I from going into a nose dive or the like.

-A still furthervery important object of the invention resides in the provision of an improvement of this nature which is simple in its construction, inexpensive to install, easy to manipulate, thoroughly eificient and reliable in use, and otherwise well adapted to the purpose for which it is designed.

With the above and numerous other objects in view, as will appear as the description proceeds, the invention resides in certain novel features of construction, and in the combination and arrangement of parts as will be hereinafter more fully described and claimed.

In the drawing: a

Figure 1 is a side elevation of an aeroplane embodying the features of my invention,

Figure 2 is a fragmentary top plan view thereof,

Figure 3 is a fragmentary vertical longitudinal section therethrough taken substantially on the line 33 of Figure 2,

Figure 4 is a transverse detail section taken substantially on the line 4-4 of Figure 1,

Figure 5 is another transverse detail section taken substantially on the line 5-5 of Figure 1,

Figure 6 is an enlarged detail section taken Figure 7 is a similar section taken substan- "zially on the line 7-7 of Figure 6.

Referring to the drawing indetail, it will be seen that the numeral 5 denotes a fuselage adapted to be supported in the air by wings 6 in the usual well known manner. Although I have shown a biplane structure in the drawings it is to be understood that a monoplane structure or any other I of the well known structures may be utilized as this feature is not of the essence of the invention. I

A shaft 7 is journaled across the. fuselage immediately to the rear of the cockpit 8 and has auxiliary wings 9 on the outer ends thereof to rock freely on this shaft; A rod 10 extends through the intermediate portions of the auxiliary wings 9, and through arcuate guide ways 11 provided in the sides of the fuselage. Collars 12 on the rod prevents lateral movement of this rod as is apparent from an inspection of :Figure 5. A pairof cranks 14 extend from the rod within the fuselage and have links 15 pivotally connected therewith and extending forwardly.

A sleeve 16 is rockable on the shaft 7 within the fuselage and has a pair of cranks 17 with which the forward ends of the links 15 are pivotally engaged.

A link 18 is pivotally engaged with one of the cranks 17 and extends forwardly to a control lever 19 pivotally mounted as at 20' inthe cockpit and having a detent' structure 21 thereon to engage in a notch 22 provided in a bracket 23.

Obviously by rocking the lever 19 the trailing edge of the edges of the auxiliary wings 9 can be elevated or lowered from the normal substantially horizontal position indicated in Figure 1. When in this normal position as just described recesses of V-shaped formation that when suflicient pressure is brought to} bear against the lever 19 in either direction-L .1

the bolts will be released from the notches or tails of construction, and in thecombination and arrangement of parts may be resorted to without departing from the spirit or scope of the. invention as hereinafter claimed or sacrificing any of its advantages.

Having thus described my invent1on, what I claim as new is:

1. In an aeroplane, a fuselage, a main wing auxiliary.

supporting structure, a palr of I wings one to each side of the fuselage to the rear of the main supporting wing structure, a shaft through the fuselage and through the entering edges of the auxiliary Wings for rockably mounting said auxiliary wings, a sleeve rockably mounted on the shaft'within the fuselage, a crank extending from said sleeve, a rod connecting the intermediate portions of the auxiliary wings and extending through arcuate guideway slots in the fuselage, a crank on said rod, a link connecting the crank, means for rocking the first mentioned crank for elevating or depressing the wings. I

2. In an aeroplane, a fuselage, a main wing supporting structure, a air of auxiliary wings one'to each side oflt e fuselage to the rear of the main supporting wing structure, a shaft through the fuselage and through the entering edges of the auxiliary Wings for rockably mounting said auxiliary wings, a sleeve rockably mounted on the shaft within the fuselage, a crank extending from said sleeve, a rod connecting the'intermediate portions of the auxiliary wings and extending through arcuate guideway slots in the fuselage, a crank on saidrod, a link connecting the crank, a link extending forwardly from the first mentioned crank, an operating lever rockably mounted in the fuselage and connected with the lastment-ioned link. 3. In an aeroplane, a fuselage, a main wing supporting structure for the fuselage, a shaft through the fuselage in the rear of the main supporting structure extending be yond the sides thereof, a pair of auxiliary wings having their entrance edges rockably mounted on the extremities of the shaft, arcuate guideway members in the sides of the fuselage, and a rod extending from the auxiliary wings and through the guideways.

4. In an aeroplane, a fuselage, a main Wing supporting structure for the fuselage,

a shaft through the fuselage in the rear of themain supporting structure extendln i e yond the-sides thereof, a pair of auxi iary wings having their entrance edges rockably mounted on the extremities of the shaft,

arcuate guideway members in the sides of the fuselage, and a rod extending from the auxiliary wings andthrough the guideways, means for swinging the wings in different angles; i

5. In an aeroplane, a fuselage, a main Wing supporting structure for the fuselage a shaft through the fuselage in the rear 0' the main supporting structure extending beyond the sides thereof, a pair of auxiliary wings having their entrance'edges rockably mounted on the extremities of the shaft, arcuate guideway members in the sides of the fuselage, and a rod extending from the auxiliary wings and through the guideways, a sleeve rockable on the shaft and having a crank, a crank extending from the rod, a

link connected to the crank, and means for rocking the first mentioned crank to elevate or depress the wing. v

/ 6'. In an aeroplane, a fuselage, a main wing supporting structure for the fuselage, a shaft through the fuselage in the rear of the main supporting structure extending beyond the sides thereof, a pair of auxiliary wings having their entrance edges rockably mounted on the extremities of the shaft, arcuate guideway members in' the sides of the fuselage, and a rod extending from the auxiliary wings and through the guideways, a sleeve rockable on the shaft and having a crank, a crank extending from the rod, a link connected to the crank, and means for rocking the first mentioned crank to elevate or depress the wing, said guideways having incorporated therein spring pressed bolts, said rod having notches to receive said bolts to hold the auxiliary wings in normal position in respect to the fusela e.

In testimony whereof I a x my signature.

JAMES G. CONNOR. 

